AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Cessna 120 and 140 Series Aeroplanes
AD/CESSNA 120/7 Met-Co-Aire Tricycle Landing Gear 5/2003
Applicability: Model 120, 140, and 140A aircraft, on which a Met-Co-Aire Tricycle Landing Gear (STC SA4-916) has been installed.
Requirement: 1. Tighten and torque the four AN 4 bolts (two on each side) which extend through the Cessna main gear wedges and the part number RD-1001C-11 Met-Co-Aire support plate to 50-70 inch pounds. Care should be taken to insure that the AN 365 stop nuts have not bottomed on the bolt threads before adequately tightening the wedge in place as specified above; use metal washers under the nut or bolt heads as necessary.
2. Conduct a detail visual inspection for cracks in the corners of the slots in the support plate, part number RD-1001C-11, and the attach plate. If cracks are evident, before further flight, replace cracked part with Met-Co-Aire part number RD-1001C-6 or FAA approved equivalent part. When a new part is installed, the repetitive inspection requirement for this paragraph may be discontinued.
3. Inspect the attachment of the top flanges of the bulkheads in the landing gear attachment box and check that all rivets which secure the box to the floor structure are properly installed. Rectify any rivet which is improperly installed. Refer to Met-Co-Aire installation instructions, dated 29 August 1959, revised 1 January 1961.
If installed, remove the adaptor plates, Cessna part number 0441147, which may have been used to extend the main gears forward.
Note: FAA AD 61-25-01 Amdt 376 and Met-Co-Aire Service Directive SD-1003 refer.
Compliance: For Requirements 1 and 2: Within 20 hours time in service after 15 May 2003, and thereafter at intervals not to exceed 100 hours time in service; except for Requirement 2, when a new part is installed.
For Requirement 3: Unless already accomplished, within 20 hours time in service after 15 May 2003.
This Airworthiness Directive becomes effective on 15 May 2003.
Cessna 120 and 140 Series Aeroplanes
AD/CESSNA 120/7 (continued)
Background: The FAA requires certain actions to correct an unsafe condition in the main landing gear.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 4 April 2003
The above AD is notified in the Commonwealth of Australia Gazette on 23 April 2003.
Overview
The Airworthiness Directive (AD) issued under the Civil Aviation Act 1988 was enacted to address an identified unsafe condition in the main landing gear of Cessna 120 and 140 series aeroplanes equipped with a Met-Co-Aire Tricycle Landing Gear. This AD, specifically AD/CESSNA 120/7, was introduced on 15 May 2003 by the Civil Aviation Safety Authority (CASA), following recommendations by the Federal Aviation Administration (FAA) to rectify safety concerns. The directive aims to ensure that all necessary maintenance and inspection actions are performed to maintain the airworthiness of the affected aircraft, thereby enhancing flight safety and compliance with aviation safety standards.
Scope and Application
The Airworthiness Directive issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 applies specifically to Model 120, 140, and 140A aircraft that have a Met-Co-Aire Tricycle Landing Gear (STC SA4-916) installed. This directive mandates certain corrective actions to address an identified unsafe condition related to the main landing gear. The actions required include tightening and torquing specific bolts, conducting a visual inspection for cracks in designated parts, and ensuring the proper installation of rivets in the landing gear attachment box. If cracks are found in the support plate or attach plate, the affected parts must be replaced with a Met-Co-Aire part number RD-1001C-6 or an FAA approved equivalent. Compliance with these requirements must be achieved within specified time frames, with some actions needing to be completed within 20 hours after 15 May 2003, and others at intervals not exceeding 100 hours time in service. This AD, issued by a delegate of the Civil Aviation Safety Authority, became effective on 15 May 2003, and its details were notified in the Commonwealth of Australia Gazette on 23 April 2003.
Key Provisions
The Airworthiness Directive (AD) issued under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998 applies to Model 120, 140, and 140A Cessna aircraft that have been installed with a Met-Co-Aire Tricycle Landing Gear (STC SA4-916) (s. 1). The AD mandates specific actions to address an identified unsafe condition in the main landing gear. These actions include tightening and torquing certain bolts to specified inch pounds (s. 1(a)), inspecting for and replacing any cracked parts (s. 1(b)), and ensuring proper installation of rivets securing the landing gear attachment box to the aircraft floor structure (s. 1(c)). Additionally, adaptor plates used to extend the main gear forward should be removed if installed (s. 1(d)).
The AD imposes several obligations on the parties governed by it. Owners or operators of the specified Cessna aircraft models must ensure that the required actions are taken within specific timeframes. For instance, the tightening and torquing of the specified bolts, and the inspection and replacement of cracked parts, must be performed within 20 hours of time in service after 15 May 2003, and subsequently at intervals not exceeding 100 hours of time in service (s. 3(a), (b)). The inspection and proper installation of rivets must be accomplished within 20 hours of time in service after 15 May 2003, if not already done (s. 3(c)). The AD further mandates the removal of adaptor plates, if installed, as part of the compliance requirements (s. 1(d)).
Failure to comply with the AD may result in significant legal consequences. While the AD itself does not explicitly state penalties for non-compliance, violations of the Civil Aviation Safety Regulations 1998 can lead to substantial civil and criminal penalties. Civil penalties may include fines of up to $222,200 for corporations and $44,440 for individuals, in addition to other remedies such as injunctions or orders (s. 13). Criminal penalties can result in imprisonment for up to five years, reflecting the seriousness of non-compliance with aviation safety regulations (s. 14). Ensuring adherence to the AD is therefore crucial to maintaining the safety and airworthiness of the affected aircraft.